A Generation Structure of Continuous Gas Film on the Surface of a Substrate
A substrate and air film technology, applied in the direction of engine components, machines/engines, blade support components, etc., can solve the problems that the surface of the substrate cannot be completely covered, the cooling effect of the air film is limited, and the mechanical strength of the substrate is reduced.
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Embodiment 1
[0037] In this embodiment, the base body is a turbine blade 100 . image 3 is a schematic diagram of the turbine blade, Figure 4 yes image 3 Schematic diagram of the horizontal section of the structure.
[0038] The turbine blade 100 is composed of a split body I and a split body II, wherein the split body I and the split body II are connected at a dividing line 106 to form a complete turbine blade 100 .
[0039] A surface 101 of the turbine blade 100 is provided with a plurality of grooves 105 spaced apart from each other and parallel to each other. The length of the grooves can partly or completely pass through the surface 101 of the turbine blade 100 .
[0040] Figure 5 yes Figure 4 A schematic diagram of the enlarged structure of a tank body 105 in FIG.
[0041] from Figure 5 It can be seen from the figure that each tank body includes a tank body bottom 500 and tank body side walls 600, 700; each tank body bottom is provided with a number of discrete holes 400 p...
Embodiment 2
[0049] In this embodiment, the turbine blade with film cooling structure is basically the same as the structure in Embodiment 1, except that the angle θ between the central axis of the discrete hole and the normal direction of the substrate surface 102 is 0 °; the angle α between the axis of the opening end of the groove along the depth direction and the normal line of the substrate surface 101 is 45°; H 1 :H 2 ≥2:1.
[0050] Same as Embodiment 1, after the cooling gas on the surface 102 side of the base body enters the tank body from the discrete holes, the gas from each discrete hole will not only expand and mix along the length direction of the tank body, but also diffuse, mix, and interact with each other along the depth direction of the tank body. Superposition, that is, it can be fully developed in the first part of the tank body, thereby forming a continuous and uniform positive pressure gas, and then transported to the open end to flow out from the side of the substra...
Embodiment 3
[0052] In this embodiment, the turbine blade with film cooling structure is basically the same as that in Embodiment 1, the difference is that H 1 :H 2 ≥3:1, the angle θ between the central axis of the discrete hole and the normal direction of the substrate surface 102 is 10°; the two side walls of the first part 302 are two parallel straight line segments spaced apart, each straight line segment The included angle with the groove bottom is 65°; the included angle α between the axis of the opening end of the groove along the depth direction and the normal line of the base surface 101 is 50°.
[0053] Same as Embodiment 1, after the cooling gas on the surface 102 side of the base body enters the tank body from the discrete holes, the gas from each discrete hole will not only expand and mix along the length direction of the tank body, but also diffuse, mix, and interact with each other along the depth direction of the tank body. Superposition, that is, it can be fully developed...
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